XFOIL Version 6.96 Calculated polar for: GOE 795 smoothed 1 1 Reynolds number fixed Mach number fixed xtrf = 1.000 (top) 1.000 (bottom) Mach = 0.000 Re = 1.000 e 6 Ncrit = 5.000 alpha CL CD CDp CM Top_Xtr Bot_Xtr ------ -------- --------- --------- -------- -------- -------- -11.750 -0.4969 0.12259 0.12083 -0.0146 1.0000 0.0045 -11.500 -0.5012 0.11678 0.11504 -0.0164 1.0000 0.0049 -10.500 -0.8526 0.03242 0.03015 -0.0519 1.0000 0.0048 -10.250 -0.8417 0.02773 0.02504 -0.0532 0.9984 0.0049 -10.000 -0.8227 0.02451 0.02145 -0.0542 0.9963 0.0050 -9.750 -0.7989 0.02250 0.01918 -0.0551 0.9946 0.0051 -9.500 -0.7757 0.02091 0.01736 -0.0554 0.9928 0.0052 -9.250 -0.7531 0.01924 0.01544 -0.0554 0.9903 0.0053 -9.000 -0.7274 0.01802 0.01401 -0.0558 0.9880 0.0053 -8.750 -0.7004 0.01692 0.01273 -0.0563 0.9860 0.0054 -8.500 -0.6722 0.01596 0.01160 -0.0569 0.9844 0.0055 -8.250 -0.6431 0.01505 0.01054 -0.0577 0.9831 0.0055 -8.000 -0.6209 0.01419 0.00953 -0.0568 0.9790 0.0057 -7.750 -0.5956 0.01317 0.00834 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0.4646 0.9879 2.250 0.5675 0.00619 0.00144 -0.0693 0.4194 0.9950 2.750 0.6383 0.00667 0.00164 -0.0731 0.3508 1.0000 3.250 0.6832 0.00709 0.00187 -0.0708 0.3000 1.0000 3.500 0.7051 0.00734 0.00200 -0.0697 0.2706 1.0000 3.750 0.7268 0.00762 0.00217 -0.0684 0.2397 1.0000 4.000 0.7475 0.00798 0.00236 -0.0670 0.2008 1.0000 4.250 0.7675 0.00840 0.00259 -0.0655 0.1593 1.0000 4.500 0.7874 0.00884 0.00284 -0.0640 0.1205 1.0000 4.750 0.8080 0.00923 0.00309 -0.0626 0.0914 1.0000 5.000 0.8297 0.00953 0.00332 -0.0614 0.0739 1.0000 5.250 0.8515 0.00983 0.00356 -0.0603 0.0595 1.0000 5.500 0.8731 0.01015 0.00382 -0.0590 0.0460 1.0000 5.750 0.8945 0.01049 0.00410 -0.0578 0.0345 1.0000 6.000 0.9157 0.01084 0.00440 -0.0566 0.0248 1.0000 6.250 0.9375 0.01115 0.00470 -0.0554 0.0193 1.0000 6.500 0.9589 0.01149 0.00503 -0.0542 0.0148 1.0000 6.750 0.9803 0.01183 0.00536 -0.0529 0.0121 1.0000 7.000 1.0014 0.01219 0.00573 -0.0517 0.0102 1.0000 7.250 1.0231 0.01250 0.00608 -0.0505 0.0095 1.0000 7.500 1.0442 0.01284 0.00646 -0.0493 0.0087 1.0000 7.750 1.0648 0.01323 0.00688 -0.0479 0.0080 1.0000 8.000 1.0848 0.01368 0.00735 -0.0465 0.0071 1.0000 8.250 1.1043 0.01415 0.00789 -0.0450 0.0067 1.0000 8.500 1.1252 0.01450 0.00827 -0.0438 0.0064 1.0000 8.750 1.1450 0.01492 0.00875 -0.0424 0.0061 1.0000 9.000 1.1649 0.01535 0.00921 -0.0410 0.0057 1.0000 9.250 1.1839 0.01583 0.00976 -0.0396 0.0054 1.0000 9.500 1.2023 0.01635 0.01033 -0.0380 0.0052 1.0000 9.750 1.2206 0.01686 0.01089 -0.0364 0.0048 1.0000 10.000 1.2372 0.01749 0.01158 -0.0346 0.0045 1.0000 10.250 1.2496 0.01846 0.01265 -0.0321 0.0042 1.0000 10.500 1.2662 0.01903 0.01330 -0.0303 0.0041 1.0000 10.750 1.2834 0.01954 0.01386 -0.0287 0.0040 1.0000 11.000 1.2977 0.02019 0.01459 -0.0266 0.0039 1.0000 11.250 1.3093 0.02086 0.01535 -0.0240 0.0038 1.0000 11.500 1.3226 0.02142 0.01598 -0.0218 0.0035 1.0000 11.750 1.3333 0.02217 0.01682 -0.0192 0.0034 1.0000 12.000 1.3451 0.02288 0.01760 -0.0170 0.0032 1.0000 12.250 1.3571 0.02359 0.01838 -0.0149 0.0031 1.0000 12.500 1.3673 0.02446 0.01932 -0.0127 0.0030 1.0000 12.750 1.3756 0.02548 0.02043 -0.0104 0.0029 1.0000 13.000 1.3833 0.02656 0.02161 -0.0082 0.0028 1.0000 13.250 1.3883 0.02790 0.02306 -0.0059 0.0028 1.0000 13.500 1.3948 0.02916 0.02441 -0.0041 0.0026 1.0000 13.750 1.3974 0.03081 0.02618 -0.0021 0.0026 1.0000 14.000 1.3902 0.03344 0.02898 0.0002 0.0024 1.0000 14.250 1.3928 0.03529 0.03097 0.0014 0.0024 1.0000 14.500 1.3893 0.03789 0.03370 0.0025 0.0024 1.0000 14.750 1.3765 0.04166 0.03767 0.0034 0.0023 1.0000 15.000 1.3755 0.04439 0.04052 0.0035 0.0023 1.0000 15.250 1.3703 0.04776 0.04403 0.0033 0.0023 1.0000 15.500 1.3623 0.05174 0.04815 0.0025 0.0023 1.0000 15.750 1.3558 0.05573 0.05226 0.0014 0.0023 1.0000 16.000 1.3450 0.06061 0.05730 -0.0003 0.0023 1.0000 16.250 1.3224 0.06775 0.06461 -0.0035 0.0023 1.0000 16.500 1.3063 0.07424 0.07126 -0.0066 0.0023 1.0000 16.750 1.2896 0.08123 0.07839 -0.0102 0.0023 1.0000 17.000 1.2586 0.09118 0.08850 -0.0153 0.0023 1.0000 17.250 1.2331 0.10041 0.09787 -0.0201 0.0023 1.0000 17.500 1.2064 0.11008 0.10768 -0.0249 0.0023 1.0000 17.750 1.1824 0.11940 0.11710 -0.0296 0.0023 1.0000 18.000 1.1317 0.13498 0.13283 -0.0375 0.0023 1.0000 18.250 1.1074 0.14514 0.14309 -0.0426 0.0023 1.0000 18.500 1.0766 0.15740 0.15546 -0.0489 0.0024 1.0000 18.750 1.0603 0.16637 0.16450 -0.0536 0.0024 1.0000 19.000 1.0384 0.17752 0.17574 -0.0594 0.0025 1.0000